Tunable variable emissivity materials and methods for controlling the temperature of spacecraft using tunable variable emissivity materials

ABSTRACT

Tunable variable emissivity materials, methods for fabricating tunable variable emissivity materials, and methods for controlling the temperature of a spacecraft using tunable variable emissivity materials have been provided. In an exemplary embodiment, a variable emissivity material has the formula M1 (1−(x+y)) M2 x M3 y MnO 3 , wherein M1 comprises lanthanum, praseodymium, scandium, yttrium, neodymium or samarium, M2 comprises an alkali earth metal, M3 comprises an alkali earth metal that is not M2, and x, y, and (x+y) are less than 1. The material has a critical temperature (T c ) in the range of about 270 to about 320K and a transition width is less than about 30K.

This is a Divisional of application Ser. No. 11/468,033, filed on Aug. 29, 2006 now U.S. Pat. No. 7,691,284.

FIELD OF THE INVENTION

The present invention generally relates to methods for reducing temperature extremes experienced by aerospace systems, and more particularly relates to tunable variable emissivity materials and methods for controlling the temperature of spacecraft using tunable variable emissivity materials.

BACKGROUND OF THE INVENTION

Spacecraft, such as satellites, high-altitude inflatables, and military aircraft, are exposed to a wide range of thermal conditions during service. A side facing the sun is heated by direct solar radiation, while a side facing the void of space is cooled by radiation. Thermal control of the spacecraft is therefore important. Various techniques have been developed in an attempt to maintain the interior of the spacecraft at a temperature suitable for occupancy by human beings and sensitive equipment. However, prior art techniques have displayed a number of drawbacks.

One technique for moderating the temperature of a spacecraft utilizes thermal louvers, which consist of a series of mechanically controlled metal slats that can open and close, effectively increasing and decreasing radiative heat loss, in response to the temperature of the satellite. However, thermal louvers can add excessive weight to the spacecraft, require power to operate, and can be prone to failure.

In another technique, the external surface of the spacecraft is covered with a white coating. The coating is designed to absorb very little solar radiation, yet radiate thermal energy in the infrared spectrum, thus biasing the overall temperature of the satellite structure on which it is disposed towards cooler temperatures. However, while this solution can help limit the upper temperature of the satellite under variable orbital lighting conditions, certain coatings can leave the spacecraft susceptible to large temperature fluctuations. Critical onboard components, such as batteries, can be unduly stressed by excessive cooling unless they are heated by onboard power sources.

Accordingly, it is desirable to provide a variable emissivity material that can passively reduce the temperature extremes experienced by aerospace systems. It is also desirable to provide a variable emissivity material that is lightweight and requires no additional power source to control the temperature of a spacecraft. In addition, it is desirable to provide a method for fabricating a variable emissivity material. Furthermore, other desirable features and characteristics of the present invention will become apparent from the subsequent detailed description of the invention and the appended claims, taken in conjunction with the accompanying drawings and this background of the invention.

BRIEF SUMMARY OF THE INVENTION

In accordance with an exemplary embodiment of the present invention, a variable emissivity material has the formula M1_((1−(x+y)))M2_(x)M3_(y)MnO₃, wherein M1 comprises lanthanum, praseodymium, scandium, yttrium, neodymium or samarium, M2 comprises an alkali earth metal, M3 comprises an alkali earth metal that is not M2, and x, y, and (x+y) are less than 1. The material has a critical temperature (T_(c)) in the range of about 270 to about 320K and a transition width less than about 30K.

In accordance with another exemplary embodiment of the present invention, a method for fabricating a variable emissivity material comprises selecting a first alkaline earth metal M2 and selecting a second alkaline earth metal M3, wherein M3 is not M2. The method further comprises the step of forming M1_((1−(x+y)))M2_(x)M3_(y)MnO₃, wherein M1 is selected from the group consisting of lanthanum, scandium, yttrium, praseodymium, neodymium or samarium and x, y, and (x+y) are less than 1.

In accordance with a further exemplary embodiment of the present invention, a method for controlling the temperature of a spacecraft comprises selecting a first alkaline earth metal M2 and a second alkaline earth metal M3, wherein M3 is not M2. A variable emissivity material M1_((1−(x+y)))M2_(x)M3_(y)MnO₃ is formed, wherein M1 is selected from the group consisting of lanthanum, scandium, yttrium, praseodymium, neodymium or samarium, and x, y, and (x+y) are less than 1. The variable emissivity material is applied to a component of a spacecraft.

BRIEF DESCRIPTION OF THE DRAWINGS

The present invention will hereinafter be described in conjunction with the following drawing figures, wherein like numerals denote like elements, and wherein:

FIG. 1 is a schematic diagram of the atoms of a perovskite structure;

FIG. 2 is a graph of a ferromagnetic-paramagnetic transition of a variable emissivity material in accordance with an exemplary embodiment of the present invention;

FIG. 3 is a graph of a ferromagnetic-paramagnetic transition of La_(0.7)Ba_(0.3)MnO₃;

FIG. 4 is a graph of a ferromagnetic-paramagnetic transition of La_(0.7)Be_(0.3)MnO₃;

FIG. 5 is a graph of a ferromagnetic-paramagnetic transition of La_(0.5)Ba_(0.25) Be_(0.25)MnO₃;

FIG. 6 is a contour map of the critical temperature T_(c) of La_((1−(x+y)))Ba_(x)Be_(y)MnO₃ based on the mole fraction of barium and beryllium;

FIG. 7 is a flow chart of a method for fabricating a variable emissivity material, in accordance with an exemplary embodiment of the present invention;

FIG. 8 is a flow chart of a method for fabricating a variable emissivity coating, in accordance with an exemplary embodiment of the present invention; and

FIG. 9 is a cross-sectional view of a substrate upon which is disposed a variable emissivity coating, in accordance with an exemplary embodiment of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

The following detailed description of the invention is merely exemplary in nature and is not intended to limit the invention or the application and uses of the invention. Furthermore, there is no intention to be bound by any theory presented in the preceding background of the invention or the following detailed description of the invention.

The present invention is directed to various embodiments of a tunable variable emissivity material that can be fabricated to passively reduce the temperature extremes experienced by aerospace systems, such as satellites, high-altitude inflatables, deep-spacecraft, and the like. A material with a high emissivity efficiently radiates heat while a material with a low emissivity radiates less heat. A variable emissivity material is any material that, when heated above a critical temperature T_(c), experiences a phase change that alters the material's emissivity. At the material transforms from a low emissivity metal into a high emissivity semiconductor. As a result of this behavior, the material tends to self-regulate its temperature near T_(c), radiating heat at temperatures above T_(c) and retaining heat below T_(c). The material can be applied to any surface where temperature control through radiative emission is required (e.g., satellite radiators).

In accordance with an exemplary embodiment of the present invention, a variable emissivity material can be represented by the following: M1_((1−(x+y)))M2_(x)M3_(y)MnO₃, where M1 comprises lanthanum (La), scandium (Sc), yttrium (Y), praseodymium (Pr), neodymium (Nd), or samarium (Sm) and preferably is lanthanum. M2 is an alkali earth metal and M3 is an alkali earth metal that is not M2. In a preferred embodiment of the invention, M2 comprises beryllium (Be) or magnesium (Mg), more preferably Be, and M3 comprises barium (Ba), strontium (Sr), or calcium (Ca), more preferably Ba. The sum (x+y) is less than 1.

The variable emissivity material has a perovskite oxide structure 10, such as that illustrated in FIG. 1, having oxygen (O⁻²) atoms 12, manganese (Mn⁺³ or Mn⁺⁴) atoms 14, and rare earth or other +3 transition metal ions M1 16. A certain portion of the rare earth/+3 transition metal ions M1 16 are replaced with one of two different alkali earth metal ions, M2 and M3. The variable emissivity material undergoes a metal-insulator phase transition at a critical temperature T_(c). Below T_(c), the material is metallic and ferromagnetic and exhibits a low emissivity, that is, an emissivity ε of no greater than 0.5. At temperatures above T_(c), the material behaves like a paramagnetic insulator with a high emissivity, that is ε of no less than about 0.6. Therefore, in the regime where thermal emission controls surface or structure temperature, the material tends to self regulate its temperature near T_(c). Compared to a material with a constant ε, the variable emissivity material will radiate heat quickly at temperatures greater than T_(c), thus cooling a substrate or structure upon which the material is disposed, and radiate heat slowly at temperatures below T_(c), thus retaining heat. For space applications, it is desirable to maintain components or structures of spacecraft, such as electronic components or human occupants, at about room temperature, that is, about 270K to about 320K. Accordingly, in a preferred embodiment of the invention, the variable emissivity material has a T_(c) in the range of about 270K to about 320K. In a more preferred embodiment of the invention, the variable emissivity material has a T_(c) in the range of about 290K to about 310K.

The emissivity change at T_(c) is accompanied by a magnetic (ferromagnetic-paramagnetic) transition. Accordingly, it can be detected with a Superconducting Quantum Interference Device (SQUID). As the variable emissivity material is heated in the presence of a weak magnetic field, a large drop in the magnetic moment of the material will occur as it undergoes the ferromagnetic-paramagnetic transition. FIG. 2 is a graph 50 of this transition for a variable emissivity material of the present invention, with the x-axis 52 representing temperature (in degrees Kelvin) and the y-axis 54 representing the long moment (in electromagnetic units (emu)). The transition from the ferromagnetic to the paramagnetic state is indicated by the transition curve 56. The transition width 58 is the temperature difference that occurs when the slope of the curve 58 has about the highest magnitude. The critical temperature T_(c) 60 is the approximate temperature that occurs when the transition is at its half-way point. The narrower the transition width, the more the material will bias the substrate temperature towards T_(c). In a preferred embodiment of the invention, the variable emissivity material has a transition width 58 of no more than about 30K, more preferably no more than about 20K.

The critical temperature T_(c) and the transition width of the variable emissivity material can be selected for or “tuned” to predetermined values by varying the identity and quantity of the alkali earth metal ions M2 and M3. For example, FIG. 3 is a graph 100 of the transition curve 102 of La_(0.7)Ba_(0.3)MnO₃ and FIG. 4 is a graph 120 of the transition curve 122 of La_(0.7)Be_(0.3)MnO₃. The x-axes in both figures, 110 and 130 respectively, represent the temperature of the material (in degrees Kelvin). The y-axes in the figures, 112 and 132 respectively, represent the long moment of the material (in electromagnetic units (emu)). The T_(c) 104 of La_(0.7)Ba_(0.3)MnO₃ is approximately 295K, while the T_(c) 124 of La_(0.7)Be_(0.3)MnO₃ is only about 252K. In contrast, the transition width 126 of La_(0.7)Be_(0.3)MnO₃ is much narrower, about 25K, than the transition width 106 of La_(0.7)Ba_(0.3)MnO₃, which is about 70K. For a given application, it may be desirable to fabricate a variable emissivity material that has the relatively higher T_(c) of La_(0.7)Ba_(0.3)MnO₃ and the relatively narrow transition width of La_(0.7)Be_(0.3)MnO₃. In accordance with an exemplary embodiment of the present invention, a variable emissivity material with a high T_(c) and a narrow transition width can be achieved with the specific selection of M2 and M3 and their respective mole fractions.

For example, in accordance with one embodiment of the invention, the variable emissivity material may be La_(0.5)Ba_(0.25)Be_(0.25)MnO₃. FIG. 5 is a graph 150 of the transition curve 160 of La_(0.5)Ba_(0.25)Be_(0.25)MnO₃. The x-axis 152 represents the temperature of the material in degrees Kelvin and the y-axis 154 represents the long moment of the material in electromagnetic units (emu). As illustrated in FIG. 5, La_(0.5)Ba_(0.25)Be_(0.25)MnO₃ has a relatively high T_(c) 156 of about 315K and yet has a relatively narrow transition width 158 of about 25 to 30K. FIG. 6 is a contour map 200 illustrating that by varying the mole fraction of barium (x-axis 202) and beryllium (y-axis 204) in La_(0.5)Ba_(x)Be_(y)MnO₃, T_(c) can be tuned to a desired value.

FIG. 7 illustrates a method 230 for using a variable emissivity material M1_((1−(x+y)))M2_(x)M₃ _(y)MnO₃ to control the temperature of a spacecraft. As described above, the variable emissivity material can comprise lanthanum (La), scandium (Sc), yttrium (Y), praseodymium (Pr), neodymium (Nd), or samarium (Sm), and preferably comprises lanthanum. The method comprises the step of selecting the identity of M2 and M3 and the quantity of M2 and M3, that is, x and y (step 232), and, if not already selected, M1. Preferably, the identity and quantity of M2 and M3 are selected so that the resulting variable emissivity material has a predetermined critical temperature T_(c) and a predetermined transition width. Once M2, M3, x, and y are selected, the variable emissivity material is formed (step 234) and is applied to a component of a spacecraft (step 236).

The variable emissivity material, in accordance with various embodiments of the present invention, may be formed using any suitable method. For example, the variable emissivity material may be synthesized using ion-beam doping of M1MnO₃ films with M2 and M3 atoms, oxidation of vapor-deposited stoichiometric metal films of M1, M2, M3 and Mn, or reaction under mechanically energetic conditions such as ball-milling, jar milling, or hand-grinding of reactant metal oxides M1O, M2₂O₃, M3₂O₃, and MnO₃, followed by post-annealed compositions.

FIG. 8 illustrates a method 250 for synthesizing a variable emissivity material and a variable emissivity coating comprising a variable emissivity material, in accordance with exemplary embodiments of the present invention. Method 250 comprises the step of combining acetylacetonate (C₅H₇O₂) (“acac”) ligand-complexed metal ions in a solvent according to the following equation: (1−(x+y))M1(acac)₃ +xM2(acac)₂ +yM3(acac)₂+Mn(acac)₃ M1_((1−(x+y))) M2_(x) M3_(y) MnO ₃, (step 252), to form a variable emissivity material. The solvent may be any material capable of dissolving the reactants. To form a film, the variable emissivity material may be deposited onto a binder, such as film of poly(vinyl alcohol) (PVA), and dried (step 254), The variable emissivity film then may be heat-treated to further crystallize the product (step 256). Alternatively, if the variable emissivity material is to be in the form of a powder, the material may be mixed with a PVA aqueous solution and dried (step 254). The mixture then is heat-treated to further crystallize the product (step 256). The heat-treated powder then may be mixed with an organic or inorganic binder so that it can be rolled, painted, sprayed, spin-coated, or the like onto a substrate or so that a substrate can be dipped in the mixture (step 258). As illustrated in FIG. 9, the methods 230 and 250 result in a variable emissivity coating 240 disposed on a substrate 242, where the coating comprises a variable emissivity material 244 that is coupled to the substrate via a binder 246.

The following is an example of the preparation of La_(0.5)Ba_(0.25)Be_(0.25)MnO₃ film, in accordance with an exemplary embodiment of the present invention. Lanthanum acetylacetonate (La(acac)₃.H₂0), manganese acetylacetonate (Mn(acac)₃), beryllium acetylacetonate (Be(acac)₂) and barium acetylacetonate (Ba(acac)₂) may be dissolved in a mixed 4:1 solution of propanoic acid and methanol to form a variable emissivity material. To form a film, a PVA aqueous solution (about 15%) may be spin-coated onto a substrate, and the variable emissivity material may be spin-coated on the PVA film, followed by drying at 150° C. for about 10 hours. The resulting film then may be heat-treated in air at 400 to 600° C., preferably 450 to 550° C. To form a powder, the perovskite product may be combined with a PVA aqueous solution until a viscous gel is formed (about 6 wt % PVA) and dried at about 150° C. for about 4 to about 10 hours. The resulting product then may be heat-treated in air at 1000° C. for about 5 hours. The heat-treated powder may be mixed with an inorganic or organic binder so that it can be rolled, painted, sprayed, spin-coated, or the like onto a substrate or so that a substrate can be dipped in the mixture. Suitable binders include potassium silicate, such as Kasil® available from PQ Corporation of Philadelphia, Pa., silicone-modified epoxy, polyurethane, poly(dimethylsiloxane), poly(dimethylsiloxane-co-methylphenylsiloxane), polyamide, Dow Corning® HC 2000, available from Dow Corning Corporation of Midland, Mich., or a combination thereof. For example, 300 g of the heat-treated powder may be mixed with 175 g of Kasil® and 100 g of H₂O to form an inorganic-based paint.

Accordingly, a variable emissivity material, a method for fabricating a variable emissivity material, and a method for controlling the temperature of a spacecraft using a variable emissivity material have been presented. The variable emissivity material radiates heat quickly at temperatures above the material's critical temperature T_(c) and slowly at temperatures below T_(c). The T_(c) and the transition width of the variable emissivity material can be tuned to desired values by the strategic selection of the identity and quantity of the components of the variable emissivity material. While at least one exemplary embodiment has been presented in the foregoing detailed description of the invention, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the invention in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing an exemplary embodiment of the invention, it being understood that various changes may be made in the function and arrangement of elements described in an exemplary embodiment without departing from the scope of the invention as set forth in the appended claims and their legal equivalents. 

What is claimed is:
 1. A method for controlling the temperature of a spacecraft, the method comprising: selecting a first alkaline earth metal M2; forming a variable emissivity material M1_((1−(x+y)))M2_(x)M3_(y)MnO₃, wherein: M1 is selected from the group consisting of lanthanum, scandium, yttrium, praseodymium, neodymium or samarium; x, y and (x+y) are greater than zero and less than 1; and M3 is beryllium and M2 is not M3; and applying the variable emissivity material to a component of a spacecraft.
 2. The method of claim 1, wherein selecting M2 comprises selecting M2 so that the variable emissivity material has a critical temperature (Tc) in the range of about 270 to about 320K and a transition width of no more than about 30K.
 3. The method of claim 1, wherein the forming comprises ion-beam doping of M1MnO₃ films with M2 and M3 atoms.
 4. The method of claim 1, wherein the forming and the applying are performed substantially simultaneously and wherein the forming comprises oxidizing vapor-deposited stoichiometric metal films of M1, M2, M3 and Mn.
 5. The method of claim 1, wherein the forming comprises ball-milling, jar milling, or hand-grinding reactant metal oxides M1O, M2₂O3, M3₂O₃, and MnO₃.
 6. The method of claim 1, wherein the forming comprises dissolving (1−(x+y))M1(acac)₃, xM2(acac)₂, yM3(acac)₂ and Mn(acac)₃ in a solvent to form the variable emissivity material M1_((1−(x+y)))M2_(x)M3_(y)MnO₃, wherein (acac) is acetylacetonate.
 7. The method of claim 6, further comprising: drying the variable emissivity material; and heat-treating the variable emissivity material.
 8. The method of claim 1, wherein the selecting comprises selecting M2 from the group consisting of barium, strontium, and calcium.
 9. The method of claim 1, wherein the applying the variable emissivity material to a component of the spacecraft comprises mixing the variable emissivity material with a binder comprising one selected from the group consisting of potassium silicate, silicone-modified epoxy, polyurethane, poly(dimethylsiloxane), poly(dimethylsiloxane-co-methylphenylsiloxane), polyamide, and a combination thereof.
 10. The method of claim 9, wherein applying the variable emissivity material to a component of the spacecraft comprises rolling, painting, spraying, or spin-coating the variable emissivity material/binder mixture onto the component.
 11. A method for controlling the temperature of a spacecraft, the method comprising: dissolving 0.5La(acac)₃, 0.25Ba(acac)₂, 0.25Be(acac)₂ and Mn(acac)₃ in a solvent to form a variable emissivity material La_(0.5)Ba_(0.25)Be_(0.25)MnO₃, wherein (acac) is acetylacetonates and applying the variable emissivity material to a component of a spacecraft. 